# Service Bulletin

Aerostructures 850 Lagoon Drive Chula Vista, California 91910

- 2098 

## SUMMARY

Summary 1 of 1

The information contained in this document is G oodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). NUMBER: DATE: ATA SYSTEM: 

## A318/A319/A3 20/A321 RA32071

- 160 September 18, 2014 71

- 00

- 00 CFM56

- 5A/5B

SUBJECT: 

## NACELLE

- ENGINE MOUNT

- REPETITIVE INSPECTION OF

A FT ENGINE MOUNT INNER RETAINER

BACKGROUND
Operators have reported broken aft engine mount inner retainers P/N 238

- 0252

- 505.



### ACTION

This Service Bulletin tasks operators to perform a repetitive detailed visual inspection of the aft engine mount inner retainers P/N 238

- 0252

- 505 (3 per engine) and replace if necessary.



### COMPLIANCE
Category 3
Accomplish within 12 months of: A/C delivery, inspection or installation of new retainer per SB RA32071

- 146, or issuance of this service bulletin, whichever occurs last.
Perform repetitive inspection every 12 months thereafter

. NOTE: THE INTENT O F AOT A71N001

- 12

REV 2 , SB RA32071

- 146 REV 2, EASA AD 2013

- 0050 OR FAA AD 2014

- 14

- 06 SHOULD HAVE BEEN COM PLIED WITH PRIOR TO IMPLEM ENTATION OF THIS SERVICE BULL ETIN.



### EFFECTIVITY

A ll Aft Engine Mounts on A318 /A319/A320/A321 aircraft operated with CFM56

- 5A/5B engines. 

### M A NPOWER
The estimated time to incorporate the full intent of this Service Bulletin on one Nacelle (without bootstrap use) :



### MATERIAL INFORMATION

No kit is associated with this Service Bulletin. (a) Gain Access 0.50 M/HRS (b) Inspect Retainers 0.50 M/HRS (c ) Replace Retainer(s) if necessary 1 .00 M/HRS ( d ) Put Nacelle to Service 0.50 M/HRS
Total 2.5 0 M/HRSThe information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

This Page Intentionally Left Blank

# Service Bulletin

Aerostructures 850 Lagoon Drive Chula Vista, California 91910

- 2098 

## A318/A319/A3 20/A321

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 1 of 1 3 The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Go odrich consent.

This document is subject to the controls and restrictions of the U. S. Export Administration Regulations (EAR). NACELLE

- ENGINE MOUNT

– REPETITIVE INSPECTION OF AFT ENGINE MOUNT INNER RETAINER

1. PLANNING INFORMATION

A. Effectivity (1) Airplane: A318/A319/A320/A321
(2) Engine: CFM56

- 5A/5B

(3) All three inner retainers P /N 238

- 0252

- 505 on the Aft Engine Mount

NOTE: THE INTENT OF AOT A71N001

- 12 REV 2, SB RA32071

- 146 REV 2, EASA AD 2013

- 0050 OR FAA AD 2014

- 14

- 06 SHOULD HAVE BEEN COMPLIED WITH PRIOR TO IMPLEMENTATION OF THIS SERVICE BULLETIN.

B. Reason
(1) Problem:
Aft engi ne mount inner retainers have been reported failed in service at the bend radius

. (2) Cause:
A metallurgical evaluation found the retainers have failed by a fatigue cracking mechanism.

(3) Background:

Some c ases of failed retainers have been reported.

( 4) Objective:
Inspect the aft engine mount inner retainers for cracks or failures. Remove and replace as necessary.

(5) Substantiation:
This Service Bulletin has been substantiated by engineering analysis.

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 2 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). C. Description
This Service Bulletin provides the instructions to inspect the aft engine mount inner retainers P/N 238

- 0252

- 505 for cracks or failures every 12 months and replace as necessary.

D. Compliance Category 3 Accomplish within 12 months of: A/C delivery, i nspection or installation of new retainer per SB RA32071

- 146 , or issuan ce of this service bulletin, whichever occurs last. Perform repetitive inspection every 12 months thereafter.

NOTE: THE INTENT OF AOT A71N001

- 12 REV 2, SB RA32071

- 146 REV 2, EASA AD 2013

- 0050 OR FAA AD 2014

- 14

- 06 SHOULD HAVE BEEN COMPLIED WITH PRIOR TO IMPLEMENTATION OF THIS SERVICE BULLETIN.

E. Approval The technical content of this document is approved under the authority of DOA ref. E ASA.21J.031.

F. Manpower
Estimated man

- hours to incorporate the intent of this bulletin to a Nacelle using trained personnel (without bootstrap use):

In

- Shop M

- HRS

Gain Access 0.50 Inspect Retainers 0.50 Replace Retainer(s) if necessary 1.00

Put Na celle into Service 0.50

Total 2.50

NOTE: ESTIMATED LABOR HOUR S ARE FOR PLANNING P URPOSES ONLY. LABOR REIMBURSEMENT IS NOT PROVIDED UNDER THE T ERMS OF THIS SERVICE BULLETIN.

G. Weight and Balance

None.

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 3 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). H. Electrical Load Data

Not affected.

I. Referenc es The following information was used in preparation of this Service Bulletin:

Data Identification Change Chapter/Section Type Data

AI

- CFM56S

- 140038 June 2014 71

- 20

- 00 Engineering Coordination Memo

EASA AD 2013

- 0050 March 2013

- Airworthiness Directive

FAA AD 2014

- 14

- 06 July 2014

- Airworthiness Directive

Airbus AOT A71N001

- 12 Revision 2 February 2013

- Alert Operators Transmission

238

- 0252 ADCN F

- Engineering Drawing

QN 2063462

- - Quality Notification A318/A319/A320/A321 CFM56

- 5A/ 5B Component M aintenance Manual Jul 15/12 71

- 22

- 07 Publication

A319/A320 CFM56

- 5 A Aircraft Maintenance Manual Aug 01/11 71

- 13

- 00 71

- 22

- 11 78

- 36

- 00 Publication

A318/A319/A320/A321 CFM56

- 5B Aircraft Maintenance Manual Aug 01/11 71

- 13

- 00 71

- 22

- 11 78

- 36

- 00 Publication

J. Other Publications Affected

None.

K. Interchangeability or Intermixability of Parts

Pr e and post service bulletin EBUs are interchangeable. Interchangeability and intermixability of the Aft Engine Mount Assembly is not affected.

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 4 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). 2. MATERIAL INFORMAT ION

A. Material Price and Availability (1) No kits are provided to accomplish this Service Bulletin. The following part may be required and may be purchased from Goodrich.

Part Number Nomenclature QTY ( per engine) EST’D

UNIT PRICE
238

- 0252

- 505 Inner Retainer 3 RFQ

B. Industry Support Information No industry support is provided for this service bulletin.

C. Material Necessary to Implement SB

None.

D. Materials Necessary for each Spare
Refer to sections 2.A. and 2.C.

E. Parts Affected by the Service Bulle tin

Part Number Qty Nomenclature Old P/N Qty Operation CHG Code SPRT Code

23 8

- 0252

- 505 (3) Inner Retainer 238

- 0252

- 505 (3) Inspect A 6

Note 2 : Change Codes A = New and Old Parts are directly interchangeable.

Note 3 : Support Codes 6 = New part c urrently available.

F. Tooling

Reference Nomenclature

S487ETT2 Engine Trolley

S686CR56

- 5 Engine Cradle

98D27803500001 Tool

- Zero Locking, Flap Slat CTL Lever

98D71203500000 Bootstrap

- System

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 5 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). 3. ACCOMPLISHMENT INSTRUCTIONS

A. Airplane

These instructions are writ ten on the condition that the Power Plant is installed on the airplane.
(1) Open the fan cowl doors. Ref er to A318/A319/A320/A321 CFM56

- 5A/ 5B Aircraft Maintenance Manual (AMM) Task 71

- 13

- 00

- 010

- 040.
(2) Open the thrust reverser doors. Refer to A318/319/A320/A321

- C FM56

- 5A/ 5B Aircraft Maintenance Manual (AMM) Task 78

- 36

- 00

- 010

- 040.
(3) Inspection of the Inner Retainers (3 locations)

NOTE: PAY CLOSE ATTENTION TO THE INNER BEND OF THE RETAINER.

NOTE: THE CENTER RETAINER MAY BE DIFFICULT TO INSPECT. IN

CASE OF DOUBT, REMO VE THE RETAINER AS PER SECTION 3.A.(4). FOR INSPECTION.
a) C lean any dirt or unwanted material from the aft engine mount with a lint

- free cotton cloth.
b) Without the removal of any hardware, do a visual inspection of the 238

- 0252

- 505 inner retainer for cracks using 10x magnification, mirror and light. Refer to Figure 1.
i) For retainers which are cracked or failed , replace the retainer as per 3.A.(4). Return cracked or failed hardware before next flight and the D ata C ollection and R eporting S heet (Sheet 1) back to Goodrich.
ii) For retainers without cracks and not failed , no further action is required. Proceed to step 3.A.(8).
(4) Removal of Outer Retainer s (3 locations)

NOTE: THIS TASK CAN BE ACC OMPLISHED ON WING, E VEN THOUGH

CLEARANCE IS TIGHT, USING THE FOLLOWING PR OCED URES 3.A.(4).A THROUGH 3. A.(4). C

. a) Without the use of the engine bootstrap system, remove the following parts in accordance with AMM 71

- 22

- 11

- 0 00

- 043 section 4. A. for CFM56

- 5B and AMM 71

- 22

- 11

- 000

- 042 section 4. A. for CFM56

- 5A: The NAS6303U5 bolts, the VN936NP3C washers, the VN936NP3 w ashers, and the NAS1805

- 3 nuts that attach the outer retainers to the inner retainers. Refer to Figure 2 . Retain the hardware for installation.

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 6 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). b) Remove the outer retainers 238

- 0253

- 509 and 238

- 0253

- 511 (or 238

- 0253

- 507)

. Retain the hardware for installation. Refer to Figure 2 and AMM 71

- 22

- 11

- 0 00

- 043 section 4. A. for CFM56

- 5B and AMM 71

- 22

- 11

- 000

- 042 section 4. A. for CFM56

- 5A

. c) I nspect for a gap between the pin head and anti

- rotation bracket. Refer to Figure 2 and 3.
i) If there is a gap of more than 0.001 inch (0.025mm), then proceed to step 3.A .( 5 ) because the engine weight must be supported per the Aircraft Maintenance Manual, Chapter 71

- 22

- 11.
ii) If the gap is less than 0.001 inch (0.025mm), proceed to step 3.A.( 6).
(5) Inst allation of Bootstrap

NOTE: BOOTSTRAP INSTALLATI ON IS NECESSARY ONLY IF A GAP IS

FOUND BETWEEN THE PI N HEAD AND ANTI

- ROTATION BRACKET
a) Install the Bootst rap system to take the engine w eight off of the aft engine mount. Refer to AMM Task 71

- 22

- 11

- 000

- 0 43, subtask 71

- 22

- 11

- 480

- 051 for CFM56

- 5B and AMM Task 71

- 22

- 11

- 000

- 0 4 2 , subtask 71

- 22

- 11

- 480

- 05 0 for CFM56

- 5A

. (6) Replacement of the Inner Retainers (3 locations)
a) Inspect the nuts P/N 83642

- 918 and P/N 83642

- 1420 for any looseness or wear. If loose or worn, rep lace. Record the condition of nuts in Sheet 1

. b) Apply t orque on large nut P/N 83642

- 1420 in the tightening direction with an open end type adapter or a torque wrench at 80 lbf.ft. Record if there is any movement of the nut in Sheet 1.
c) Apply torque on small nut P/N 83642

- 918 in the tightening direction with a torque wrench set at 35 lbf.ft. Record if there is any movement of the nut in Sheet 1.
d) Remove the following parts in accordance with AMM 71

- 22

- 11

- 0 00

- 043 section 4. A. for CFM56

- 5B and AMM 71

- 22

- 11

- 000

- 04 2 section 4. A. for CFM56

- 5A: t he nuts P/N 83642

- 918 and P/N 83642

- 1420. Retain for installation.
e) Remove and replace the inner retainer P/N 238

- 0252

- 505. Refer to Figure 2 and section 4. G . of AM M 71

- 22

- 11

- 000

- 043 and AMM 71

- 22

- 11

- 400

- 043 for CFM56

- 5B and section 4. G . of AMM 71

- 22

- 11

- 000

- 042 and AMM 71

- 22

- 400

- 042 for CFM56

- 5A.

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 7 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). (7) Instal lation of Outer Retainers (3 locations)
a) Instal l the following parts in accordance with AMM 71

- 22

- 11

- 400

- 043 section 4.G.11 for CFM56

- 5B and AMM 71

- 22

- 11

- 400

- 042 section 4.G.1 1 for CFM56

- 5A: The 83642

- 1420 nut, 83642

- 918 nut, 238

- 0253

- 511 (or 238

- 0253

- 507) outer retainer, 238

- 0253

- 509 outer retainer, NAS6303U5 bolts, VN936NP3C washers, VN936NP3 washers, and NAS1805

- 3 nuts.
b) If installed, remove the Bootstrap system. Refer to AMM Task 71

- 22

- 11

- 400

- 043, subtask 71

- 22

- 11

- 080

- 050 for CFM56

- 5B and AMM Task 71

- 22

- 11

- 400

- 042, subtask 71

- 22

- 11

- 080

- 051 for CFM56

- 5A.
(8) Close the thrust reverser doors. Refer to A318/319/A320/A321

- CFM56

- 5A/ 5B Aircraft Maintenance Manual (AMM) Task 78

- 36

- 00

- 4 10

- 040.
(9) Close the fan cowl doors. Refer to A318/A319/A320/A321 CFM56

- 5A/ 5B Aircraft Maintenance Manual (AMM) Task 71

- 13

- 00

- 4 10

- 040.
(10) Write in engine log and/or other records that Goodrich Service Bulletin RA32071

- 160 has been incorporated.
(11) Reinspect all reta iners P/N 238

- 0252

- 505 every 12 months in accordance with this service bulletin

. (12) If cracked or failed retainers are found, populate the data collection and reporting sheet (Sheet 1) and return with the failed retainers to Goodrich through your Aerostructur es Airline Support Manager

. B. Shop (QEC Instructions) The following instructions are for when the engine is in the shop.
(1) Follow the instructions of sections 3.A

. (3) , 3.A.(4).a.

- 3.A.(4).b., 3.A.(6 ) , 3.A.(7).
(2) Mark in the engine log that SB RA32071

- 160 has bee n accomplished.
(3) If cracked or failed retainers are found, populate the data collection and reporting sheet (Sheet 1) and return with the failed retainers to Goodrich through your Aerostructures Airline Support Manager.
(4) Reinspect all retainers P/N 238

- 0252

- 505 every 12 months in accordance with this service bulletin.

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 8 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

Inspection of Retainer Bend for C racks

Figure 1

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 9 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

Assembly and Disassembly of Retainer

Figure 2

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 10 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). Typical Engine Attach Hardware

– Gap Test Figure 3

# Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56

- 5A/5B NUMBER: RA32071

- 160
DATE: September 18, 2014 PAGE: 11 of 1 1

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent.

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). DATA COLLECTION SHEET FOR SERVICE BULLETIN RA32071

- 160 OPERATOR DATA
OPERATOR:

________ _________ DATE INSPECTED:

___________ A/C MSN:

______________ __ ___ A /C MODEL:

_____________ ____ ENGINE MODEL:

_____________ TSN:

________________ ________ CSN:

________________ TSO:

________________ CSO:

________________ ENGINE 1
S/N _____________ PLEASE INDICATE THE CONDITION OF RETAINE RS AT EACH LOCATION:
BRIGHT

OR DULL INTACT, CRACKED

OR FAILED IF CRACKED, CRACK LENGTH LEFT: CENTER: RIGHT: HISTORY OF RETAINER MAINTENANCE, IF ANY:

CONDITION OF ALL NUTS (WORN, LOOSE, ETC) :

LARGE NUT SMALL NUT LEFT: CENTER: RIGHT:

ENGINE 2
S/N _____________ PLEASE INDICATE THE CONDITION OF RETAINE RS AT EACH LOCATION:
BRIGHT

OR DULL INTACT, CRACKED

OR FAILED IF CRACKED, CRACK LENGTH LEFT: CENTER: RIGHT: HISTORY OF RETAINER MAINTENANCE, IF ANY:

CONDITION OF ALL NUTS (WORN, LOOSE, ETC):

LARGE NUT SMALL NUT LEFT : CENTER: RIGHT:

Data Collection and Reporting Sheet

Sheet 1